Flight systems must be validated to show that they are consistent with the requirements of their intended applications. While high reliability is difficult to validate, the additional complexity of fault tolerance further compounds the validation problem. The objective of NASA's research is to develop a methodology for designing validatable fault-tolerant systems. Under this design-for-validation philosophy, emphasis is placed on developing validation methods that can be incorporated into the design process right from the start and design methods and guidelines which, while incorporating fault tolerance, can assure validatability. This paper examines the statistical issues of validating highly reliable, fault-tolerant systems. There are many problems associated with traditional methods of designing and validating these potentially complex hardware and software systems. Useful design-for-validation methods, which include structured specification and design methodologies, mathematical proof techniques, analytical modeling, simulation and emulation, and physical testing, are discussed. Important design issues associated with fault tolerance are presented along with the related validation concerns which must be addressed. Experience has shown that synchronization and Byzantine resilience must accompany fault tolerance. Other design attributes associated with fault tolerance may be used by a designer on the basis of cost, weight, performance, and validation considerations.


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    Title :

    Design and validation of fault-tolerant flight systems


    Additional title:

    Konstruktion und Bewertung fehlertoleranter Flugsysteme


    Contributors:

    Published in:

    AIAA-Papers ; Sep ; 1-7


    Publication date :

    1987


    Size :

    7 Seiten, 37 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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